Mounting for aircraft motors



Feb. 9, 1932. H. c. oTwl-:LL

MOUNTING FOR AIRCRAFT MOTORS Filed June 7. 1930 R. E W M W .M ww

W v ATTORNEYS,

Patented Feb. 9, 1932 HIRAM CANNON OTWELL, OF SAN FRANCISCO, CALIFORNIAMOUNTING FOR AIRCRAFT MOTORS Application led June 7, 1930. Serial No.459,664.

rlhe present invention rela-tes to mountings for aircraft motors, and isapplicable to flying machines of any type using either one or aplurality of motors. lfl The principal object of the invention is toprovide means for tilting the axis of the .propeller to any desiredangle without necessitating a flexible connection between the propellerand its driving motor. For this purpose the entire motor is mounted fortilting to the desired angle. A second object of the invention is toprovide a strong and rigid mounting for holding the motor in its variouspositions, and which will allow it to be easily tilted from one positionto another. A still further object is to provide simple and easilyoperated means for tilting the motor, which can be applied to aplurality of motors to enable them to be tilted simultaneously. Stillanother object is to provide means for supplying fuel to the motor inall its positions. Other objects of the invention will become apparentfrom the following specification.

Although my invention may be applied to single motored airplanes, itwill find its bestuse in planes having a plurality of motors. In suchmachines, some of the motors may be permanently mounted to provideforward propelling force, and others arranged for `tilting to inclinedor vertical positions, so that they may be used to assist in taking oliand landing, or in emergencies, by providing an upward pulling force. Insuch cases it is naturally desirable that the motors, both fixed andtiltable, be symmetrically positioned with respect to the longitudinalcenter of the plane; for example, in a machine having four motors, twoon each side; one motor on each side should be fixed and the othertiltable. It is not my intention, however, to limit the invention to anyspecific number or arrangement of motors.

The invention is most easily applied to airplanes of the type having oneor more radial cylinder motors mounted above the uppermost wing, and forthis reason it has been so illustrated inthe drawings. It will beunderstood, however, that the invention may be applied to other types ofaircraft and to other forms of motors, and further that the form,

construction and arrangement of the several parts may be varied withinthe limits of the claims hereto appended without departing from thespirit of the invention as expressed therein. y y 155` Apreferred'embodiment of the invention is illustrated in the accompanyingdrawings, wherein Fig. l is a front elevation, partly in section, of theupper wing of an airplane and the upper portion of the fuselage, showingtwo motors mounted above said wing.

Fig. 2 is a side elevation of one of the motors, showing it in bothhorizontal and vertical positions, certain portions of the motor framebeing shown in section.

Fig. 3 is a horizontal section taken mainly on the line 3-3 of Fig. 2.

Fig. 4 is a sectional detail taken on the line LA of Fig. 3. y 70 In thedrawings, the reference numeral 5 designates the upper wing of anairplane, and 6 is the cabin or fuselage. Any number of motors,indicated diagrammatically by the numeral 7, may be mounted above thewing 5, each driving a propeller 8. In order to simplify the drawings, Ihave shown two motors both of which are similarly mounted and adaptedfor tilting. In as much as the radial type of motor is best adapted tomy mounting I have illustrated motors of this type.

In the preferred mounting, the motor 7, Figs. 2 and 3, is secured in anyusual manner to the forward end of a frame 9, which is 95 fixed upon atransverse horizontal shaft 10. The ends of said shaft are journaled instandards 11 rising from and rigidly secured to the wing 5. The rear4end of the frame 9 is narrowed for stream-lining elfect, and providesboth a guide for the movementof said frame and a lock for holding it inany of its desired positions. The entire frame is preferably covered bya shell 12.

An arcuate guide member 13 of channel 95 section is rigidly mount-ed in`any desired manner., as for example bybeing secured at its lower end toa cross member 14 extending between the forward legs of the standardsl1, and at its upper end to braces 15 extending rearwardly and upwardlyfrom said standards. The rear end of the motor frame 9 has an extension16`which travels within the channel of the guide 13, as the frame swingsfrom its horizontal position shown in full lines in Fig. 2 to itsvertical position, shown in dotted lines. A strap 17 passes freelyaround the outside of the channel member13, and has its endssecured tothe frame 9, as indicated in Fig. 3, thus preventing any possibleseparat-ion betweenthe end of said frame and the guide13. A n

The guide 13 has within its channel a niember 18 provided with notches19 adapted for engagement by the rear end of a slidable bolt 2O carriedwithin the end 16 oflthe frame 9. The forward end of said bolt isslidably guided by a bracket 20', and it is normally held in engagementwith the notch 19 by a spring 21, thereby locking the frame 9 securelyin position. The bolt is withdrawn from said notch by a cam 22 freelyrotatable about the supporting shaft 10. rlhe'cam operates a rod 23which-is connected with the bolt 2O by a lever 24, the latter beingfulcrumed at 25 in the frameY 9.v The cam 22 is rotated byv a link 26,Figs. 1 and 4, which is connected with anarm 27 extending from a shaft28 mounted preferably within the wing 5. If a plurality of motors are tobe controlled simultaneously, each may be similarly connected with theshaft `28 as shown in Fig. 1. An arm 29, extending rearwardly from saidshaft, is connected by a link 30 with a suitable operating lever 31within the fuselage 6. It will be observedvthat if the motor is in ahorizontal position andthe cam is shiftedto the position shown in dottedlines in Fig. 4, the bolt 2O will be withdrawn, thereby allowing themotor and its frame 9 to be swung about t-he axis of the shaft 10. Whenthe cam following rod 23 rides off the lower end of the cam 22` thespring 21 causes the bolt 20 to engage the next notch 19 to which theswinging of the motor frame carries it, so that, by properly positioningthe cam 22, the swinging movement of the motor frame can be arrested atthe desired position. Y

Any suitable means may be provided for tilting the mot-or.V As anexample of a preferred means I have shown` a sprocket 32 secured uponthemotor supporting shaft 10, and connected by a chain 33 with a similarsprocket upon a transverse shaft 34, the latter being iournaled insuitable bearings 35. A worm wheel 36'is secured uponthe shaft 34 and isturned by a worm 37 operated by a shaft 38 and hand wheely 39 within thefuselage 6. The shaft 38 is understood to haveY suitable bearings, notshown.V If a plurality of motors are Vto be `tilted simultaneously,asshown inFig. 1, each is connected The above described mechanism providesa strong and easily operated means for tilting the motor or motors, andis sufficiently flexible so that its operation is not affected by theusual vibration of the motor and its mounting. When the bolt 20 isengaged with one of the notches 19 in the guide member, the motor issecurely held against movement in any direction and can be operated atfull power without movement upon its tilting axis. It is intended that,before releasing the bolt 20 to permit the tilting of the motor, itshould be 'throttled down to idling speed. The chain and worm wheeltilting mechanism described should be of suflicient strength and powerto tilt the motor easily while it is running at slowspeed. l a

In order to supply fuel to the motor in all' its positions, I prefer toemploy-a fuel pipe 40, Fig. 3, which has a portion of its length coiledinto a helix 41 and positioned coaxially with the supporting shaft 10.VA suitable l0- cation forsaid helix is within the shaft 10, which ispreferably hollow in order to reduce its weight. By making the helix 41with a sufficient number ofv turns, the amount t of bending of the pipeat any one point is well within the elastic limit of any suitable metal.The pipe, after leaving the helix 41, passes through the wall ofthetubular shaft 10 and continues forwardly to the motor. By positioningthe helix within thev shaft 10 it is entirely protected from lmechanicalinjury. The portion of the pipe leading to the helix maybe supported inany convenient manner not shown in the drawings. n

1. In a flying machine having amotorand a propeller driven thereby, aframe to which said motor is secured, saidV frame having'a rearwardextension; means for mounting-said frame to permit swinging movementthereof; a fixed arcuate guide member of channel cross section withinwhich said extension travels, said guide member having spaced notches; astrap secured to said frame-and freely surrounding said guide member toretain said extensionin association therewith; and a locking membercarried by said extension and adapted for engagement with said notches.

2.- In ai flying machine having a motor and a propeller driven thereby,a frameto which 'said' motor is secured; means for'mounting said framefor swinging movement; Aa fixed arcuate guide with which said frame ismove ably associated; a locking member carried by said frame forengagement with said guide; a clam mounted about the axis of movementofsaid frame; means operated by said cam for controlling said lockingmember; and means for moving said cam. l 3.V In a iying machine having amotor and propeller driven thereby, a frame, upon Y which saidmotor iscarried; a tubular support about which said frame is mounted forswinging movement; and a conduit for sup plying fuel to said motor, saidconduit having a coiled portion Within said tubular sup port permittingit to Hex with the swinging of said frame.

1l. In a lyng machine having a Wing, a fuselage below said Wing, and amotor and propeller above said Wing; a frame to which 10 said motor issecured; a pivotal mounting for said frame; and means for swinging Saidvframe comprising a sprocket. associated therewith, a shaft in the upperportion of said fuselage, a chain connecting said shaft with saidsprocket, a Worm Wheel secured to said shaft, a Worm engaging saidWheel, and means Within the fuselage for rotating said Worm.

In testimony whereof I have signed my name to this specification.

il@ HIRAM CANNON OTWELL.

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